Specific heating ratio (Cp/Cv) =
Mach number =
Canopy Reference Area =
Canopy Mouth (inlet) Area =
Polar Porosity (%) =
Lateral Porosity (%) =
Fabric Air Permeability (l/sq.m/s) =
Input data in fields above and click --->
Drag coefficient =
Dynamic pressure Cp =
Base pressure Cp =
The drag prediction is valid for rigid isolated axisymmetric perforated shell. Note, that real flexible parachute operates in forebody turbulent wake, its influence in supersonic case is very strong and can cause the canopy pulsing and even collapse.
Nevertheless, if this code is used to evaluate the drag coefficient of real parachute, the inlet area must be defined from experiment or with the aid of structural code (ex. MONSTR-2.2). An arbitrary canopy must be presented as axisymmetric one with appropriate polar and lateral porosity.
The local prorosity is presented as porous area with respect to reference area. It is assumed, the lateral porosity (usually - gaps and ring slots) is located near midsection.